机匣处理作用下高负荷轴流压气机转/静子匹配设计研究
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摘要
为了探索机匣处理作用下转/静子的轴向匹配方法以进一步提高压气机级的失速裕度,研究了静子的叶型安装角及"弯"、"掠"规律对压气机性能的影响,针对机匣处理与优化静子的组合结构进行了非定常数值模拟,阐述了该结构的扩稳机理以及压气机新的失速机制。研究结果表明,在机匣处理作用下,静子成为压气机失速的触发因素,通过对静子叶型安装角及"弯"、"掠"规律的优化均可进一步提高压气机级的失速裕度,其中改变静子"弯"型对压气机级失速裕度的改善最大。组合应用机匣处理与尖部反弯根部正弯静子后,压气机效率基本不变,失速裕度提升了80.2%,较单独使用机匣处理提升30.9%。在该组合结构作用下,压气机的失速由静子触发,静子叶根吸力面在激波作用下发生附面层分离,且与轮毂表面附面层相互作用形成角区涡,接近失速边界时,静子叶根形成"前缘溢流,尾缘反流"现象,造成静子通道的大范围堵塞,诱发压气机失速。压气机级的扩稳应充分考虑机匣处理的影响,对静子进行优化设计。
In order to investigate the method of axial matching of rotor/stator on a high-loaded axial flow compressor with casing treatment for a further improvement of compressor stability,the effects on compressor performance of the installation angle and the laws of sweep and lean of stators were numerically studied. The flow mechanism of stability improvement was analyzed with the method of unsteady simulations for the combination of casing treatment and optimized stator,and the compressor's stall mechanism was also studied. The results show that the stall of the compressor is triggered by the compressor stator. The compressor's stability can be improved further by optimizing the installation angle or the sweep and lean laws of stators. The stability enhancement is maximized by optimizing the lean law of stators. The compressor's stability is improved by 80.2% and the adiabatic efficiency remains unchanged by the combination of casing treatment and re-designed stator with positively curved blade tip and negatively curved blade root. The compressor stability is improved further by 30.9% compared with the case with only casing treatment. The compressor's stall is triggered by the stator. The boundary layer of suction surface at stator's root is separated under the effect of passage shock. It interacts with the boundary layer of hub surface resulting in a corner vortex. The flow phenomenon of"leading edge spillage,trailing edge backflow"is observed at the operating condition of near stall. The induced blockage in the stator triggers the compressor's stall. The stator should be optimized for a compressor stage under the effect of casing treatment to achieve a better stability improvement.
In order to investigate the method of axial matching of rotor/stator on a high-loaded axial flow compressor with casing treatment for a further improvement of compressor stability,the effects on compressor performance of the installation angle and the laws of sweep and lean of stators were numerically studied. The flow mechanism of stability improvement was analyzed with the method of unsteady simulations for the combination of casing treatment and optimized stator,and the compressor's stall mechanism was also studied. The results show that the stall of the compressor is triggered by the compressor stator. The compressor's stability can be improved further by optimizing the installation angle or the sweep and lean laws of stators. The stability enhancement is maximized by optimizing the lean law of stators. The compressor's stability is improved by 80.2% and the adiabatic efficiency remains unchanged by the combination of casing treatment and re-designed stator with positively curved blade tip and negatively curved blade root. The compressor stability is improved further by 30.9% compared with the case with only casing treatment. The compressor's stall is triggered by the stator. The boundary layer of suction surface at stator's root is separated under the effect of passage shock. It interacts with the boundary layer of hub surface resulting in a corner vortex. The flow phenomenon of"leading edge spillage,trailing edge backflow"is observed at the operating condition of near stall. The induced blockage in the stator triggers the compressor's stall. The stator should be optimized for a compressor stage under the effect of casing treatment to achieve a better stability improvement.
引文
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[2]Hathaway MD.Passive Endwall Treatments for Enhancing Stability[R].NASA-TM-2007-214409.
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[4]Lu Xingen,Chu Wuli,Zhu Junqiang,et al.Numerical Investigations of the Coupled Flow Through a Subsonic Compressor Rotor and Axial Skewed Slot[J].Journal of Turbomachinery,2009,131(1).
[5]Ma Ning,Nan Xi,Lin Feng.Numerical Study on Effects of Axial-Slot Casing Treatment on Peak Efficiency of Axial Compressors[R].ASME GT 2016-56554.
[6]刘建勇,袁巍,陆亚钧.周向局部处理机匣对压气机影响的数值研究[J].航空动力学报,2010,25(7):1609-1614.
[7]李继超,林峰,刘乐,等.跨音轴流压气机自循环喷气扩稳试验研究[J].机械工程学报,2014,50(8):135-143.
[8]Yang H,Nuernberger D,Nicke E,et al.Numerical Investigation of Casing Treatment Mechanisms with a Conservative Mixed-Cell Approach[R].ASME GT 2003-38483.
[9]Weichert S,Day I,Freeman C.Self-Regulating Casing Treatment for Axial Compressor Stability Enhancement[R].ASME GT 2011-46042.
[10]Wang Wei,Chu Wuli,Zhang Haoguang,et al.Experimental Study of Self-Recirculating Casing Treatment in a Subsonic Axial Compressor[J].Proceedings of the Institution of Mechanical Engineers,Part A:Journal of Power and Energy,2016,230(8):805-818.
[11]Greitzer E M,Nikkanen J P,Haddad D E,et al.A Fundamental Criterion for the Application of Rotor Casing Treatment[J].Journal of Fluids Engineering,1979,101:237-243.
[12]Cheng P,Prell M E,Greitzer E M,et al.Effects of Compressor Hub Treatment on Stator Stall and Pressure Rise[J].AIAA Journal of Aircraft,1984,21(7):469-475.
[13]Heinichen F,Gummer V,Schiffer H P.Numerical Investigation of a Single Circumferential Groove Casing Treatment on Three Different Compressor Rotors[R].ASME GT 2011-4590.
[14]Wilke I,Kau H-P,Brignole G.Numerically Aided Design of a High-Efficient Casing Treatment for a Transonic Compressor[R].ASME GT 2005-68993.
[15]Matthias R,Martin L,Konrad V,et al.Experimental and Numerical Investigation of a Circumferential Groove Casing Treatment in a Low Speed Axial Research Compressor at Different Tip Clearances[R].ASME GT 2017-6305.
[16]王永明,胡骏,屠宝锋,等.带处理机匣的跨声速风扇非定常数值模拟[J].南京航空航天大学学报,2006,38(5):540-544.
[17]Cumpsty N A.Compressor Aerodynamics[M].Melbourne:Krieger Pub Co,2004:1-522.
[18]Hah C.Effects of Unsteady Flow Interactions on the Performance of a Highly-Loaded Transonic Compressor Stage[R].ASME GT 2015-43389.
[19]王维,楚武利,张皓光.高负荷两级轴流压气机耦合型机匣处理的设计研究[J].推进技术,2017,38(10):2365-2373.(WANG Wei,CHU Wu-li,ZHANG Hao-guang.Study of the Design of a Coupled Casing Treatment for a Two-Stage High-Loaded Axial Flow Compressor[J].Journal of Propulsion Technology,2017,38(10):2365-2373.)
[20]吴虎,黄健,高双林.处理机匣结构对某型跨声速轴流压气机畸变响应特性影响[J].西北工业大学学报,2005,23(5):26-30.
[21]马文生,顾春伟.轴流压气机跨声级转子叶顶喷气的流动特性[J].推进技术,2009,30(3):302-307.(MA Wen-sheng,GU Chun-wei.Tip Injection in Transonic Axial Compressor Rotor[J].Journal of Propulsion Technology,2009,30(3):302-307.)
[22]Hiller S-J,Matzgeller R,Horn W.Stability Enhancement of a Multistage Compressor by Air Injection[J].Journal of Turbomachinery,2011,133(3).
[2]Hathaway MD.Passive Endwall Treatments for Enhancing Stability[R].NASA-TM-2007-214409.
[3]张燕东,陆亚钧.圆弧斜槽处理机匣的实验研究[J].航空动力学报,1998,13(3):254-258.
[4]Lu Xingen,Chu Wuli,Zhu Junqiang,et al.Numerical Investigations of the Coupled Flow Through a Subsonic Compressor Rotor and Axial Skewed Slot[J].Journal of Turbomachinery,2009,131(1).
[5]Ma Ning,Nan Xi,Lin Feng.Numerical Study on Effects of Axial-Slot Casing Treatment on Peak Efficiency of Axial Compressors[R].ASME GT 2016-56554.
[6]刘建勇,袁巍,陆亚钧.周向局部处理机匣对压气机影响的数值研究[J].航空动力学报,2010,25(7):1609-1614.
[7]李继超,林峰,刘乐,等.跨音轴流压气机自循环喷气扩稳试验研究[J].机械工程学报,2014,50(8):135-143.
[8]Yang H,Nuernberger D,Nicke E,et al.Numerical Investigation of Casing Treatment Mechanisms with a Conservative Mixed-Cell Approach[R].ASME GT 2003-38483.
[9]Weichert S,Day I,Freeman C.Self-Regulating Casing Treatment for Axial Compressor Stability Enhancement[R].ASME GT 2011-46042.
[10]Wang Wei,Chu Wuli,Zhang Haoguang,et al.Experimental Study of Self-Recirculating Casing Treatment in a Subsonic Axial Compressor[J].Proceedings of the Institution of Mechanical Engineers,Part A:Journal of Power and Energy,2016,230(8):805-818.
[11]Greitzer E M,Nikkanen J P,Haddad D E,et al.A Fundamental Criterion for the Application of Rotor Casing Treatment[J].Journal of Fluids Engineering,1979,101:237-243.
[12]Cheng P,Prell M E,Greitzer E M,et al.Effects of Compressor Hub Treatment on Stator Stall and Pressure Rise[J].AIAA Journal of Aircraft,1984,21(7):469-475.
[13]Heinichen F,Gummer V,Schiffer H P.Numerical Investigation of a Single Circumferential Groove Casing Treatment on Three Different Compressor Rotors[R].ASME GT 2011-4590.
[14]Wilke I,Kau H-P,Brignole G.Numerically Aided Design of a High-Efficient Casing Treatment for a Transonic Compressor[R].ASME GT 2005-68993.
[15]Matthias R,Martin L,Konrad V,et al.Experimental and Numerical Investigation of a Circumferential Groove Casing Treatment in a Low Speed Axial Research Compressor at Different Tip Clearances[R].ASME GT 2017-6305.
[16]王永明,胡骏,屠宝锋,等.带处理机匣的跨声速风扇非定常数值模拟[J].南京航空航天大学学报,2006,38(5):540-544.
[17]Cumpsty N A.Compressor Aerodynamics[M].Melbourne:Krieger Pub Co,2004:1-522.
[18]Hah C.Effects of Unsteady Flow Interactions on the Performance of a Highly-Loaded Transonic Compressor Stage[R].ASME GT 2015-43389.
[19]王维,楚武利,张皓光.高负荷两级轴流压气机耦合型机匣处理的设计研究[J].推进技术,2017,38(10):2365-2373.(WANG Wei,CHU Wu-li,ZHANG Hao-guang.Study of the Design of a Coupled Casing Treatment for a Two-Stage High-Loaded Axial Flow Compressor[J].Journal of Propulsion Technology,2017,38(10):2365-2373.)
[20]吴虎,黄健,高双林.处理机匣结构对某型跨声速轴流压气机畸变响应特性影响[J].西北工业大学学报,2005,23(5):26-30.
[21]马文生,顾春伟.轴流压气机跨声级转子叶顶喷气的流动特性[J].推进技术,2009,30(3):302-307.(MA Wen-sheng,GU Chun-wei.Tip Injection in Transonic Axial Compressor Rotor[J].Journal of Propulsion Technology,2009,30(3):302-307.)
[22]Hiller S-J,Matzgeller R,Horn W.Stability Enhancement of a Multistage Compressor by Air Injection[J].Journal of Turbomachinery,2011,133(3).